Airplane



Jan. 15, 1929. A 1,698,853

' c. K. MORTON AI'RPLANE Filed Sept. l6, 1927 2 Sheets-Sheet 1 INVENTOR#W 1 ATTORNEYS Jan. 15,1929.

AIRPLANE C. K.. MORTQN Filed Sept. 16, 1927 2 Sheets-Sheet 2 a 4 f) 3226 38 5 i 26 A 4 a A x E 55 DOWN INVENTOR BY aluw/eaf/yorion ATTORN EYSPatented Jan. 15, 1929.

UNITED STATES PATENT OFFICE.

CHARLES R. HORTON, OF CLEVELAND, OHIO, ASSIGNOR TO THE GLENN L. MARTINCOMPANY, OF OLEVELAND,OHIO, A CORPORATION OF OHIO.

AIRPLANE.

Application filed September 16, 1927. Serial No. 219,889.

This invention relates to improvements in airplanes, but has referenceparticularl to means for adjusting the horizontal stabi izer or anyother part of considerable size which it may be desirable to adjust.

One object .of the invention is the provision 01fl means which shallrender it possible for t e airp ane to build up gradually, by the use ofsmall manuel impulses, the power necessary to make the adjustments abovereferred to.

Another object of the invention is the provision of means for readilyreversing'the direction of the adjustment to be performed andfor.locking the stabilizer'or like adjusted part in any desiredposition.

Other objects and features of novelty will appear as' I proceed with thedescription of that embodiment of the invention which, for

the purposes of the present application, I

have illustrated in the accompanying drawing, in which Fig. 1 is adiagrammatic view illustrating a horizontal stabilizer and hydraulicapparatus for adjusting the same, the actuating parts shown mounted uponthe instrument board of the plane;

' Fig. 2 is a fragmentary front elevation of the instrument board;

Fig. 3 is a detailed view on a larger scale of a fluidpump or compressorwhich may be employed in connection with the invention, some of theparts being shownin section on the line 3-3 Fig. 1;

Fig. 4 is a side elevation of a-power cylinder, the piston of which maybe connected with the stabilizer to be adjusted;

Fig. 5 is a longitudinal sectional view taken substantially on the line55 Fig. 4;

Fig. 6 is a central sectional .view of a hollow' casting enclosing oneend of the pump and upon which the valve parts are supported;

Fig-7 is asimilajr: view of similar parts at the opposite end of; thepump;

Fig. 8 is across section on the line 88 Fi 6;

showmg one of the check valves which may be employed;

Fig. 10 is a front elevation of a pair of gear sectors used incontrolling the apparatus;

Fig. 11 is an edge viewof the same;

Fig. 12 is a view, partly in section, throu h the instrument boardshowing the means f br ilot or other member of the crew of an.

1 tively.

actuating the shaft upon which the upper pa1r of sectors are mounted;and i Fig. 13 is a face view of the operating hand le shown in Fig. 12with its extreme positions indicated by dotted lines.

In the drawn) ,fragments of the airplane frame Work are s own at 10 and11. To this framework is hinged at 12 a stabilizer 13, while anelevatorl l is hinged to the rear end of the stabilizer. A link 15connects the "stabilizer near its forward or free end to a piston rod16. carr ing a piston. 17 that moves in a power cylm er 18 secured tothe frame the cylinder 18 a tubular conductor 19 extends forward to thecockpit'of the plane, and a similar conductor 20 extends forward fromthe lower endof the cylinder.

While in its broader aspects my invention is independent of anyparticular type of pump or compressor, I'prefer to employ a doubleworkof the plane. From the upper endlof acting piston pump as shown in thedrawing.

The pump cylinder 21 is mounted by any suitable means directly inadvance of the instrument board 22 on the plane. The piston 23 ismounted at the end of a piston rod 24 which projects through one end ofthe pump and through an opening in the instrument board 22,, beingprovided at its outer extremity with a handle 25 by means of which thepiston may be manuallyreciprocated.

The cylinder 21 is closed at its rear end by a hollow casting 26 whichis separated into two'compartments by a dividing wall 27 At the oppositeend of the cylinder there is a similar hollow casting 28 with a dividingwall 29. The upper and lower chambers of the casting 26 have externallthreaded bosses 30 and 31, respectively, whi e the correspondingchambers of the casting 28 have similar bosses 32 and 33. All of thesebosses have drilled openings therethrough, and the two upper bularconductors 19 and 20 are attached by i 9 1s a detailed view on a largescale suitable unions to yokes 34 and 35, respec- Through the inner wallof each of the castings 26 and 28 there are one or more holes 36 abovethe dividing wall 27 or 29, as the case may be, and a similar number ofholes 37 below the dividing wall. A disk 38 closely engages the innerwall of casting 26, the engaging surfaces being machined for thatpurpose, the disk being held in position by an inturned flange on a ring39 which is threaded onto the casting. A similar disk 40 is similarlymounted on casting 28 by means of a flanged ring 41. The disks 38 and 40each have passages therethrough which are adapted to register with theholes 36 and 37 in the casting, when the disk is rotated into either oneof two positions 180 apart. Where four holes and passages are employed,as in the form illustrated, two of the passages in each disk areprovided with ball check valves 42 opening toward the cylinder 21 andthe other two passages with check valves 43 opening away from thecylinder.

The disk 38 is arranged to be rotated by a shaft 44 which is mounted ina bearing formed in a central enlargement of the divicung wall 27, beingprovided with a threaded end portion of reduced diameter which ex-.tends through a central opening in the disk 38, and the latter beingclamped in place a nut 45. with the shaft 44, and in order thatoscillation or partial rotation may be imparted to it the shaft 44carries a gear sector 46 on its outer extremity. The disk 40 mountedupon casting 28 is threaded upon a sleeve 47 and held in position by alock nut 48. The piston rod 24 extends through this sleeve, and each ismovable independently of the other. On its outer extremity the sleevecarries a gear sector 49 substantially identical with gear sector 46 andheld in position by nuts 50 threaded upon the sleeve.

The two sectors 46 and 49 mesh with sectors 51 and 52 which are pinnedto a rock shaft 53 that extends through the instrument board 22 abovethe piston rod 24, where it is provided with an operating lever 54. Apair of stops 55 limit the throw of the lever 54. When the latter standsat one limit of its motion the inwardly opening check valves registerwith the holes in the castings 26 and 28 above the dividing walls andthe outwardly opening check valves register with the holes below thedividing walls, while when the lever 54 is thrown to the opposite limitof its motion the inwardly opening valves register with the holes belowthe dividing walls and the outwardly opening valves with the holesabovethe dividing walls. In the intermediate position of the lever 54the holes through the casting walls are closed by the disks.

In Fig. 9 I have illustrated one form of .ball check valve which may beemployed. The ball 56 is movable within the main portion 57 of thepassage through the disk and seatsup0n the inner end of-a reducedportion 58 of the passage, being urged toward its seat by a coil spring59 which abuts at the opposite end against a ring 60 that is threadedinto the disk at the end of the main portion The disk 38 is free torotate.

neeasrsa 57 of the passage. The valves 42 and 43 here tofore mentionedmay be identical with the structure shownin F ig; 9, exceptthat they arereversely arranged in the disks.-

Assuming that it becomes desirable to depress the forward edge of thestabilizer 13, pressure fluid must be admitted to the upper end of powercylinder l8through tubular connection 19, and a corresponding exhaust offluid must take place from the lower end of cylinder 18 out throughtubular connection 20; To this end the lever 54 must be thrown to anextreme position such that the disks 38 and 40 shall be brought into thepositions illustrated in Figs. 6 and 7. The sectors 51 and 52 are soproportioned to the' sectors 46 .and 49, in the present disclosure, thata quarter turn of the former will actuate the latter through half arevolution. The operator then reciprocates the handle 25 until thedesired adjustment is reached. As the piston 23 moves toward the left inFig. 3 the lower right-hand valves 42 open, permitting fluid to enterthe cylinder from conductor 20, while the upper left-hand valves 43 opento permit fluid to pass from the cylinder into the conductor 19. As thepiston 23 moves in the opposite direction, the 'lower left-hand valves42 open permitting fluid to enter the cylinder from conductor 20, whilethe upper right-hand valves 43 open permit ting the piston to forcefluid out of the cylinder into conductor 19. The pumping is discontinuedafter. the desired adjustment has been reached, and then the lever 54 isturned into its midway position, thereby carrying the fluid passages indisks 38 and 40 out of register with the holes in thecastings 26, 28.Now should it later be desired to elevate the forward edge of thestabilizer, the lever 54 is thrown to the opposite extreme positionreversing the arrangement of the check valves and the pump againoperated.

The movement of pressure fluid in the system is thus reversed and thepiston 17 is moved upwardly to an extent proportionate to the operationof the piston 23. When the proper adjustment is reached the lever isagain brought back to the intermediate position, thereby cutting off thetubular connections 19 and 20 from each other and also from the pump.

The comparative diameters of the pistons 23 and 17 should, of course, beproportioned to the load ut upon the latter by the stabilizer 13 underying conditions. In the drawing I have made no attempt to illustratethese .parts to scale. In fact the piston 17 will be much larger thanthe piston 23 in order to bring about a power advantage. As ressurefluid I employ oil, but other liqui s might be substituted. Air or someother as might be used, but it is ordinarily pre erable to employ aliquid rather thana compressible fluid for this purpose, for the reasonthat the 40 said cylinder, pump and conductors forming liquid willpositively hold the stabilizer in adjusted position.

If it should be found desirable under some conditions to hold thestabilizer or other adjusted part in position resiliently, then aircould be advantageously employe Having thus described my invention, I

' claim ,near the free end of said member, a piston therefor connectedto said member, a fluid pump, tubular conductors extending from oppositeends of said cylinder to said pump,

said cylinder, pump and conductors forming a closed system, and means atthe pump for reversing the direction of flow of fluid. 3. In anairplane, a stabilizer comprising a hinged member, a fluid-cylinderlocated near the free end of said member, a piston therefor connected tosaid member, a fluid pump, tubular conductors extending from oppositeends of said cylinder to said pump, said cylinder, pump and conductorsforming a closed system, and means at the pump for cutting ofi' oneconductor from the other.

4. In an airplane, a stabilizer comprising a hinged member, a fluidcylinder located near thefree end of said member, apiston thereforconnected to said member, a fluid pump, tubular conductors extendingfrom opposite ends of said cylinder to said pump,

a closed system, and means for disconnecting the pumpfrom both of saidconductors.

' 5.--In an airplane, a stabilizer comprising a hinged member, a fluidcylinder located near the free end of said member, a piston thereforconnected to said member, a fluid pump, tubular conductors extendingfrom opposite ends of said cylinder to said pump, said cylinder, pumpand conductors forming a closed system, and common means for reversingthe flow of fluid or for disconnecting the pump from both of saidconductors.

6. In an airplane, a'stabilizer comprising a hinged member, a fluidcylinder located near the free end of said member, a piston thereforconnected to said member, a pump cylinder and double-acting piston, atubular conductor connecting each end of said first named cylinder toboth ends of said pump cylinder, valve means at both ends of said pumpcylinder for reversing the direction of flow through said pump, andcommon means for actuating both of said valve means.

7. In an airplane, a stabilizer comprising a hinged member, a fluidcylinder located near the free end of said member, a piston thereforconnected to said member, a pump cylinder and double-acting piston, atubular conductor connecting each end of said first named cylinder toboth ends of said pump' cylinder, valve means at both ends of said pumpcylinder for reversing the direction of flow through said pump and forcutting olf the pump from said conductors, and common means foractuating-both of said valve means.

'8. In an airplane, a stabilizer comprising a hinged member, afluid-cylinder located near the free end of said member, a pistontherefor'connected to said member, a fluid pump, tubular conductorsextending from opposite ends 'of said cylinder to said pump, saidcylinder, pump and conductors forming a closed system, and said meanscomprising a rotatable" disk carrying a pair of oppositely opening checkvalves.

In testimony whereof, I hereunto afiix my signature.

CHARLES K. MORTON.

